-trajectory deviation mode (VOR, NAV, ILS)
-guidance mode ON or OFF (Flight Director bars or Flight Path Director)
-altitude reference selection (baro setting).
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DMC Output Bus - Attitude Comparison
Figure 010
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FCU - AFS & EFIS Control
Figure 011
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EFIS Control Section
Figure 012
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(4) ECAM Controls (Ref. Fig. 005, 013)
(a) ECAM control panel The ECAM control panel (ECP) allows the selection of the display on the ECAM DUs as far as the A/C system/status images are concerned. The ECAM control panel enables:
-manual selection of any A/C system diagram
-sequential display of all the A/C system pages by means of the ALL key.
(b) Transfer pushbutton switches Several types of manual transfer will be left at the disposal of the pilots:
-EIS DMC transfer, CAPT/3 or F/O/3, for EFIS and ECAM (DMC 3 taking over in case of DMC 1 or DMC 2 failure)
-ECAM-ND transfer, on the CAPT side or the F/O side. These transfers are made by means of selector switches installed on the center pedestal.
-PFD-ND transfer on the CAPT side and on the F/O side. This transfer is controlled by means of PFD-ND XFR pushbuttons located between the PFD and ND brightness/ON-OFF controls.
(c) Control and brightness knobs (Ref. Fig. 014) Situated on the left of the CAPT PFD and on the right of the F/O PFD for the EFIS DUs and on the ECAM CP for the ECAM DUs, they provide brightness control (stroke and raster) of the DUs, in conjunction with the automatic brightness control, and also the ON/OFF control. An additional brightness control knob is provided for the NDs only: it provides separate brightness control for the WXR image.
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ECAM CP - EIS DMC SWITCHING Panel
Figure 013
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PFD/ND Brightness - ON/OFF Control PFD/ND Transfer
Figure 014
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B. System Architecture and Interface The system architecture has been designed in a way as to ensure an actual segregation between EFIS, engine indicating system and ECAM information, although each DMC receives all three kinds of information. The EIS components receive from the aircraft systems all the information necessary for the elaboration of the various EFIS and ECAM displays. For the DMC, note that all the signals from the various sensors are sent in parallel to the concerned EIS equipment of side 1 and 2 (and possibly 3 for the DMCs). In fact, all the signals entering the DMCs are acquired redundantly. For example, the DMC 1 receives signals from A/C systems, computers and sensors of the side 1 and of the side 2, and identically for the DMC 2.
R **ON A/C 051-099,
(Ref. Fig. 015)
R **ON A/C 001-049, 101-105, 151-199, 201-299, 301-302,
R (Ref. Fig. 016)
R **ON A/C 001-049, 051-099, 101-105, 151-199, 201-299, 301-302,
This principle of redundancy provides numerous advantages:
-no operational degradation in case of loss of an EIS computer and simple reconfiguration.
-reliable presentation on CRTs of A/C system configuration and status, which allows simplifying the A/C system panels, and particularly the overhead panel
-simple procedures
-homogeneity in data acquisition and processing. Each main instrument panel comprises two display units, one PFD and one ND, on which the images elaborated by the DMCs from aircraft sensor data are displayed. Each DMC controls simultaneously the two display units (and also in addition one ECAM display unit). The pilots have at their disposal control devices, for selection of various reference values and display modes on their PFD and ND, and selector switches for reconfiguration of displays or input sensors in case of failure.
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